CN205380190U - Aviation is with processing bush - Google Patents
Aviation is with processing bush Download PDFInfo
- Publication number
- CN205380190U CN205380190U CN201620128588.3U CN201620128588U CN205380190U CN 205380190 U CN205380190 U CN 205380190U CN 201620128588 U CN201620128588 U CN 201620128588U CN 205380190 U CN205380190 U CN 205380190U
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- CN
- China
- Prior art keywords
- lining
- bush
- jacket wall
- crack
- flange
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Abstract
The utility model discloses an aviation is with processing bush, the bush includes the bush wall of tube -shape, wherein, has seted up on the bush wall and has cracked, is provided with the turn -ups at bush wall both ends, the bush wall encloses into a straight section of thick bamboo, crack and crack for the axial, the turn -ups is the turn -ups of the convex transition to turning up, the bush adopts polytetrafluoroethylene to be raw materials, the preferred polytetrafluoroethylene that modifies that is. This bush simple structure, easily production, and convenient to use, this bush has good wearability, corrosion resistance and ageing resistance simultaneously.
Description
Technical field
This utility model relates to hole cold extrusion strengthening field of tool, particularly relates to a kind of lining, especially, relates to a kind of aviation processing lining.
Background technology
Present generation aircraft is operated in a complex environment, the restriction of external load, environment, anthropic factor and economic dispatch each side can be subject to, for making aircraft adapt to the acute variation of these operating environments, and extend the military service phase of aircraft, FAR25.571 annex 45 Qiang Zhiyaoqius use " fail safe standard " in aircaft configuration design of major parts, in maintenance plan, adds the inspection requirements of " damage tolerance " simultaneously.
Under normal circumstances, adopting cold-extrusion technology to improve the connector life-span, cold extrusion is the reinforcement process that aircraft zero/assembly assembles all kinds of connection securing members, the top layer of Strengthening Hole can be applied effective residual compressive stress, the endurance cracking resistance energy in hole is greatly improved.And Cold-Expanded Hole typically requires and utilizes lining to realize, therefore lining is based on damage tolerance requirements and develops and develop.By the application of lining, it is possible not only to improve the fatigue life of fastener hole, and the service lifetime of aircraft can be greatly shortened.
Traditional lining can be used for aluminum, middle strength steel, titanium, nickel alloy and high strength steel, but is not suitable for the superposition material containing composite, and corrosion resistance, ageing resistance also have to be strengthened.
Utility model content
In order to overcome the problems referred to above, present inventor has performed and study with keen determination, design a kind of aviation processing lining.
Specifically, the purpose of this utility model is in that to provide following aspect:
(1) a kind of aviation processing lining, wherein, described lining includes the jacket wall 1 of tubular, wherein,
Jacket wall 1 offers and cracks 2,
Optionally, the jacket wall of 2 both sides of cracking offers the opening 3 of the radial direction for stationary bushing,
The two ends of lining are provided with flange 4；
(2) lining according to above-mentioned (1), wherein,
Described lining is straight-tube shape, and/or,
The internal diameter of described lining is 4～50mm, and/or,
The length of described lining is 10～80mm；
(3) lining according to above-mentioned (1), wherein,
The thickness of described jacket wall 1 is 1～3mm；
(4) lining according to above-mentioned (1) or (3), wherein, offers in jacket wall 1 and axial cracks 2, described in crack and 2 crack for rectangle；
(5) lining according to above-mentioned (4) or (5), wherein, described in crack 2 width be 0.5-2.5mm；
(6) lining according to above-mentioned (1), wherein, the length of described opening 3 is 4-8mm, and the width of described opening 3 is 1-1.4mm.
(7) lining according to above-mentioned (1), wherein, is provided with turned-out flange 4 at the two ends of tubular liner, and described flange 4 is circular arc transition；
(8) lining according to above-mentioned (7), wherein, the central angle of described flange 4 is 90～160 °；
(9) lining according to above-mentioned (7) or (8), wherein,
The thickness of described flange 4 is 1-3mm；
The width of described flange 4 is 2-6mm.
(10) lining according to above-mentioned (1), wherein, described lining adopts politef to be raw material.
This utility model is had the advantage that to include:
(1) described bush structure is simple, it is easy to produce, and easy to use；
(2) described lining adopts politef to be raw material so that it is is used to not only aluminum, middle strength steel, titanium, nickel alloy and high strength steel, is also applied for the superposition material containing composite；
(3) described lining has good wearability, corrosion resistance and ageing resistance.
Accompanying drawing explanation
Fig. 1 illustrates the longitudinal section view of the lining according to a kind of preferred implementation of this utility model；
Fig. 2 illustrates the axial, cross-sectional view of the lining according to a kind of preferred implementation of this utility model；
Fig. 3 illustrates that first hole is carried out lining cold-stamped schematic diagram by the lining according to a kind of preferred implementation of this utility model.
Drawing reference numeral illustrates:
1-jacket wall
2-cracks
3-opening
4-flange
5-lining
6-plug
7-front cover component
8-workpiece
9-draws rifle assembly
Detailed description of the invention
Below by drawings and Examples, this utility model is further described.Being illustrated by these, feature of the present utility model and advantage will become more apparent from clearly.
Word " exemplary " special here means " as example, embodiment or illustrative ".Here should not necessarily be construed as preferred or advantageous over other embodiments as any embodiment illustrated by " exemplary ".Although the various aspects of embodiment shown in the drawings, but unless otherwise indicated, it is not necessary to accompanying drawing drawn to scale.
According to a kind of aviation processing lining that this utility model provides, as shown in Figure 1 and Figure 2, described lining includes jacket wall 1, offers and crack 2 in jacket wall 1, the jacket wall of 2 both sides of cracking offers the opening 3 of the radial direction for stationary bushing, and the two ends of lining are provided with flange 4.
In a preferred embodiment, described lining is straight-tube shape, and jacket wall 1 is equal to the distance in lining axle center.
In a preferred embodiment, the internal diameter of described lining is 4-50mm.
In further preferred embodiment, the internal diameter of described lining is 8-20mm.
Further preferred embodiment in, the internal diameter of described lining is 10mm.
In a preferred embodiment, the length of described lining is 10-80mm.
In further preferred embodiment, the length of described lining is 10-40mm.
Further preferred embodiment in, the length of described lining is 20mm.
In a preferred embodiment, the thickness of described jacket wall 1 is 1-3mm.
Wherein, the internal diameter of lining and length to match with the diameter of Cold-Expanded Hole and thickness of slab.Insert thickness is fixed with the size of insert diameter, should not be too thick, when lining is blocked up, can be difficult to because it is hardening when preparing minor diameter slotted liner bushing, and extruding plug penetrates the difficulty of lining and also promotes accordingly.
In a preferred embodiment, jacket wall 1 offers axial crack 2.
In further preferred embodiment, described in crack 2 rectangular rectangles.
Further preferred embodiment in, described in crack 2 width be 0.5-2.5mm, it is preferred to 1-2mm.
Wherein, offering cracks is conducive to being sheathed in plug by lining, simplifies operating process.
In a preferred embodiment, offering opening 3 in the jacket wall of 2 both sides of cracking, when assembling, described opening 3 fastens the effect to play stationary bushing with workpiece.
In further preferred embodiment, the length of described opening 3 is 4-8mm, and the width of described opening 3 is 1-1.4mm.
Further preferred embodiment in, the length of described opening 3 is 6mm, and the width of described opening 3 is 1.2mm.
In a preferred embodiment, being provided with turned-out flange 4 at the two ends of tubular liner, described flange 4 is circular arc transition.
In further preferred embodiment, the central angle of described flange 4 is 90～160 °, it is preferred to 90～120 °, more preferably 90 °.
Further preferred embodiment in, the thickness of described flange 4 is 1-3mm, and width is 2-6mm.
Wherein, flange plays the effect of stationary bushing in Cold Extrusion Process, it is prevented that it produces relative motion due to the axially-movable of plug with hole wall.
Described lining is used for cold-extrusion technology, and when not change structure form, material and weight, structure is important and key position hole carries out reinforcement process process.As it is shown on figure 3, for first hole is carried out lining cold-stamped schematic diagram, wherein, be contained on plug 6 by lining 5, then lining 5 and plug 6 are injected just hole, front cover component 7 is pressed on workpiece 8, by drawing rifle assembly 9 that first hole is carried out cold extrusion.In lining Cold Extrusion Process, the acting body of lining adds the operability of cold extrusion strengthening now, particularly when opening character difference, it is possible to monolateral complete cold extrusion intensified operation；Directly contact with hole wall owing to avoiding extruding plug, decrease hole wall and scratch and aperture material stacking；Improve amount of compression, the radial compression amount produced by extruding plug is efficient, be delivered evenly to fastener hole inwall, is converted into residual stress.
In a preferred embodiment, described lining adopts politef to be raw material.
In further preferred embodiment, with polyflon (PTFE) after die pressing sintering makes stock, turnery processing is adopted to make polytetrafluoroethylene bushing.
Wherein, politef is commonly called as " King ", has excellent chemical stability, corrosion resistance, sealing, height lubricate not viscosity electrical insulating property and good aging resistance endurance, can long-term work at the temperature of+250 DEG C to-180 DEG C.Its heat resistance is fabulous, and melt temperature is 324 DEG C, and decomposition temperature is 415 DEG C, and maximum operation (service) temperature is 250 DEG C, and brittle temperature is-190 DEG C, and heat distortion temperature (when 0.46MPa) is 120 DEG C.The good mechanical properties of PTFE, its hot strength is 21～28MPa, bending strength is 11～14MPa, percentage elongation is 250%～300%, the coefficient of kinetic friction and confficient of static friction to steel are 0.04, than nylon (PA-6), polyformaldehyde (POM), polyester plastics coefficient of friction all little, concrete numerical value is in Table 1.
The comparison of the kinematics and static friction coefficient of table 1, politef (PTFE) and other engineering plastics.
| Plastics title | Confficient of static friction | The coefficient of kinetic friction |
| Politef (PTFE) | 0.04 | 0.04 |
| Nylon (PA-6) | 0.18 | 0.22 |
| Kematal (POM) | 0.14 | 0.23 |
| Dibutyl terephthalate (PBT) | 0.16 | 0.21 |
Pure politef (PTFE) intensity is low, wear no resistance and creep resistant is bad, typically require and in politef, add some without grade particles, its mechanical property is improved such as graphite, molybdenum bisuphide, aluminium sesquioxide, glass or carbon fiber etc., the method blended with other polymer such as polybenzoate (PHB), polyphenylene sulfide (PPS), polyether-ether-ketone (PEEK), poly-perfluor (ethylene/propene) copolymer (PFEP) etc. can also be utilized to extend its damping temperature range, improve its creep resistant.
In a preferred embodiment, the manufacturing process of polytetrafluoroethylene bushing comprises the following steps:
Step 1, raw material sieve: polytetrafluoroethylsuspending suspending fine powder raw material is undertaken smashing to pieces by high-speed mixer, mix, stirred, then sieves, obtain the standby raw material of politef；
Step 2, blank make: standby for above-mentioned politef raw material is made the cylindrical blank of hollow by die pressing, and the blank after the demoulding is placed the internal stress of a period of time elimination blank；
Step 3, sintering: blank step 2 obtained is positioned in sintering furnace, be sintered, cool down and obtain blank；
Step 4, machining: adopt special numerically controlled automatic lathe, filler is carried out branch's machine-shaping.
In further preferred embodiment, in step 1, the vibrosieve adopting 200 orders is sieved；In step 2, place 20～24 hours in the environment of 45～55 DEG C；In step 3, in numerical control sintering furnace, carry out the sintering of 48～96 hours by the program set.
Further preferred embodiment in, by special detection equipment each workpiece carried out the performance detections such as size, hardness, heat resistance and smoothness.
Wherein, make lining with politef and both can adjust the seal pressure between sealing surface, can ensure that again the sealing of entrance end.Simultaneously as polytetrafluoroethylene bushing has high self lubricity, it is also possible in the equipment that can not add lubricant.Further, the feature such as it has wide temperature range, wearability is good, chemical stability is excellent, oil resistivity is good, coefficient of friction is little and ageing properties is excellent.
In description of the present utility model, it should be noted that, term " on ", " front ", " interior ", the orientation of the instruction such as " outward " or position relationship be based on the orientation in this utility model accompanying drawing or position relationship, it is for only for ease of description this utility model and simplifies description, rather than the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to restriction of the present utility model.
Above in association with preferred embodiment this utility model being illustrated, but these embodiments are only exemplary, only play illustrative effect.On this basis, it is possible to this utility model carries out multiple replacement and improvement, these each fall within protection domain of the present utility model.
Claims (10)
1. an aviation processing lining, it is characterised in that described lining includes the jacket wall (1) of tubular, wherein,
Jacket wall (1) offers crack (2)；
Optionally, the jacket wall of (2) both sides of cracking offers the opening (3) of the radial direction for stationary bushing；
The two ends of jacket wall (1) are provided with flange (4).
2. lining according to claim 1, it is characterised in that
Described lining is straight-tube shape, and/or,
The internal diameter of described lining is 4-50mm；And/or,
The length of described lining is 10-80mm.
3. lining according to claim 1, it is characterised in that
Described jacket wall (1) surrounds a straight tube；And/or
The thickness of described jacket wall (1) is 1-3mm.
4. the lining according to claim 1 or 3, it is characterised in that offer axial crack (2) in jacket wall (1), described in crack (2) crack for rectangle.
5. lining according to claim 4, it is characterised in that described in the crack width of (2) be 0.5-2.5mm.
6. lining according to claim 1, it is characterised in that the length of described opening (3) is 4-8mm, the width of described opening (3) is 1-1.4mm.
7. lining according to claim 1, it is characterised in that be provided with turned-out flange (4) at the two ends of tubular liner, described flange (4) is circular arc transition.
8. lining according to claim 7, it is characterised in that the central angle of described flange (4) is 90～160 °.
9. the lining according to claim 7 or 8, it is characterised in that
The thickness of described flange (4) is 1-3mm
The width of described flange (4) is 2～6mm.
10. lining according to claim 1, it is characterised in that described lining adopts politef to be raw material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620128588.3U CN205380190U (en) | 2016-02-18 | 2016-02-18 | Aviation is with processing bush |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620128588.3U CN205380190U (en) | 2016-02-18 | 2016-02-18 | Aviation is with processing bush |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205380190U true CN205380190U (en) | 2016-07-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620128588.3U Expired - Fee Related CN205380190U (en) | 2016-02-18 | 2016-02-18 | Aviation is with processing bush |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205380190U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108193191A (en) * | 2018-01-02 | 2018-06-22 | 京东方科技集团股份有限公司 | Mask plate and preparation method thereof |
| CN113601111A (en) * | 2021-07-21 | 2021-11-05 | 南京航空航天大学 | Method for processing multi-slot bushing |
-
2016
- 2016-02-18 CN CN201620128588.3U patent/CN205380190U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108193191A (en) * | 2018-01-02 | 2018-06-22 | 京东方科技集团股份有限公司 | Mask plate and preparation method thereof |
| CN113601111A (en) * | 2021-07-21 | 2021-11-05 | 南京航空航天大学 | Method for processing multi-slot bushing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160713 Termination date: 20210218 |